CN102672972A - Preparation method for fiber composite material reinforcing strip - Google Patents
Preparation method for fiber composite material reinforcing strip Download PDFInfo
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- CN102672972A CN102672972A CN2012101656767A CN201210165676A CN102672972A CN 102672972 A CN102672972 A CN 102672972A CN 2012101656767 A CN2012101656767 A CN 2012101656767A CN 201210165676 A CN201210165676 A CN 201210165676A CN 102672972 A CN102672972 A CN 102672972A
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Abstract
The invention provides a preparation method for a fiber composite material reinforcing strip and relates to a preparation method for an inflating extending arm reinforcing strip. By the preparation method, the problems that the elastic reinforcing steel strip in the conventional charging extending arm is magnetized easily and the unit mass is high are solved. The preparation method for the fiber composite material reinforcing strip comprises the following steps of: 1, paving bottom layer Vectran fiber cloth; 2, brushing epoxy resin glue on the surface of the bottom layer Vectran fiber cloth; 3, paving interlayer carbon fiber cloth; 4, brushing epoxy resin glue on the surface of the interlayer carbon fiber cloth; 5, paving upper layer Vectran fiber cloth; 6, placing the three layers of composite fiber cloth into a special die, placing into a constant-temperature chamber, heating and curing; and 7, cutting the cured three layers of composite fiber cloth to obtain the fiber composite material reinforcing strip. The preparation method for the fiber composite material reinforcing strip has a simple process. The reinforcing strip has corrosion resistance, ageing resistance, light weight, high straightness and high tensile strength and bending rigidity, and is not magnetized. The fiber composite material reinforcing strip is applied to the charging extending arm.
Description
Technical field
The present invention relates to inflate the preparation method that extending arm strengthens bar.
Background technology
Elasticity strengthens steel bar and on satellite, is prone to be magnetized in the existing inflation extending arm, and the magnetic torque that the inflating expanded back of extending arm produces can exert an influence to the attitude of satellite, and elasticity to strengthen the density of steel bar big, unit mass is high.This existing steel bar is prone to be magnetized and the light-weighted problem of implementation structure in order to solve.
Summary of the invention
The present invention will solve elasticity in the existing inflation extending arm and strengthen the problem that steel bar is prone to be magnetized and unit mass is high, and provides a kind of fibrous composite to strengthen the preparation method of bar.
The preparation method that fibrous composite of the present invention strengthens bar carries out according to the following steps:
One, shop fixtures layer Vectran cloth: bottom Vectran cloth is tiled on the horizontal operation table top, guarantees that cloth do not have prestressing force in the face;
Two, brush coating: along bottom Vectran cloth length direction, the even brush ring epoxy resins glue on bottom Vectran cloth surface;
Three, intermediate layer, shop carbon cloth: carbon cloth is paved, sticked on the bottom Vectran cloth top of handling, obtain two-layer complex fabric cloth through step 2;
Four, brush coating: arriving of step 3 the even brush ring epoxy resins glue in carbon cloth surface of two-layer complex fabric cloth;
Five, spread a layer Vectran cloth: upper strata Vectran cloth is paved, stick on the carbon cloth top of handling, obtain three layers of complex fabric cloth through step 4;
Six, evenly brush the PRM releasing agent at the formpiston of particular manufacturing craft and the cavity surface of former, three layers of composite fibre that step 5 is obtained are arranged in the particular manufacturing craft, and the particular manufacturing craft that three layers of complex fabric cloth will be housed is then put into thermostatic chamber; Heating rate with 1～2 ℃/h is warming up to 90 ℃; Insulation 2h, the heating rate with 1～2 ℃/h is warming up to 150 ℃ again, behind the insulation 3h; Naturally cool to room temperature, three layers of complex fabric cloth that obtain solidifying;
It is the rectangular of circular arc that three layers of complex fabric cloth of the curing that seven, step 6 is obtained are cut into cross section along the impression of mould, obtains fibrous composite and strengthens bar.
The invention provides the enhancing bar that a kind of Vectran fiber/carbon fiber/Vectran fiber 3-layer composite material is processed, in order to improve bending rigidity, its cross section is designed to arc.Compound after the hot setting of Vectran fiber/carbon fiber/three layers of fibrous material layer of Vectran fiber processes.
The invention has the beneficial effects as follows: production technology of the present invention is simple; It is to be processed by Vectran fiber/carbon fiber/Vectran fiber 3-layer composite material that prepared fibrous composite strengthens bar; Corrosion-resistant, anti-aging, and can not be magnetized; Can not produce magnetic torque during as the gravity gradient boom on the satellite, can not exert an influence spacecraft attitude; The carbon fiber that fibrous composite strengthens the bar intermediate layer has high specific strength, high ratio modulus characteristics; Its stretch-proof and bending stiffness are high; Make to strengthen bar and have good elasticity and recoverability, the hot strength that strengthens bar is greater than 1500MPa, the inflation extending arm after the expansion have certain stability; Strengthen sliver transvers section and be designed to arc, improve bending rigidity; The two-layer Vectran fiber up and down that fibrous composite of the present invention strengthens bar has very high toughness, easy fracture not, can make fibrous composite strengthen bar and have less gathering volume.Fibrous composite strengthens the in light weight of bar, and the wide enhancing bar line density of 15mm is less than 15g/m; Fibrous composite enhancing bar linearity of the present invention is high, guarantees that curling the folding of inflation extending arm still has higher linearity after inflating expanded.
Fibrous composite of the present invention strengthens bar and can be applicable to inflate extending arm, and the length that fibrous composite strengthens bar can be designed to tens meters, satisfies the needs of overlength extending arm; The inflation extending arm adopts the folded form of curling, and each circle after folding gathering the in directly bonds together through hasp, puts into packing case; After emission got into space, to the hold down gag release, the air-filled pore that covers through the termination charged into gas to tube interior; Gas pressure is peeled off hasp; Drive the inflation extending arm and launch fully, reach duty, to strengthen that bar light weight, bending rigidity are big, pliability can be curled well folding draws in for fibrous composite, nonmagnetic.
The prepared fibrous composite of the present invention strengthens the isostructural expansion driving mechanism of sky shade that bar can be used for gravity gradient boom, solar sail, solar energy sailboard, large aperture antenna, super long type one pole and dipole antenna, satellite truss structure, large-scale high-precision optical mirror.
Description of drawings
Fig. 1 is a particular manufacturing craft schematic cross-section of the present invention;
Fig. 2 is the vertical view of particular manufacturing craft former 2 of the present invention;
Fig. 3 is the outer contour 7 formed circular arc sketch mapes of the cross section of convex epirelief 4 on the particular manufacturing craft formpiston 1 of the present invention.
The specific embodiment
Technical scheme of the present invention is not limited to the following cited specific embodiment, also comprises the combination in any between each specific embodiment.
The specific embodiment one: the preparation method that this embodiment fibrous composite strengthens bar carries out according to the following steps:
One, shop fixtures layer Vectran cloth: bottom Vectran cloth is tiled on the horizontal operation table top, guarantees that cloth do not have prestressing force in the face;
Two, brush coating: along bottom Vectran cloth length direction, the even brush ring epoxy resins glue on bottom Vectran cloth surface;
Three, intermediate layer, shop carbon cloth: carbon cloth is paved, sticked on the bottom Vectran cloth top of handling, obtain two-layer complex fabric cloth through step 2;
Four, brush coating: arriving of step 3 the even brush ring epoxy resins glue in carbon cloth surface of two-layer complex fabric cloth;
Five, spread a layer Vectran cloth: upper strata Vectran cloth is paved, stick on the carbon cloth top of handling, obtain three layers of complex fabric cloth through step 4;
Six, evenly brush the PRM releasing agent at the formpiston 1 of particular manufacturing craft and the cavity surface of former 2, three layers of composite fibre that step 5 is obtained are arranged in the particular manufacturing craft, and the particular manufacturing craft that three layers of complex fabric cloth will be housed is then put into thermostatic chamber; Heating rate with 1～2 ℃/h is warming up to 90 ℃; Insulation 2h, the heating rate with 1～2 ℃/h is warming up to 150 ℃ again, behind the insulation 3h; Naturally cool to room temperature, three layers of complex fabric cloth that obtain solidifying;
It is the rectangular of circular arc that three layers of complex fabric cloth of the curing that seven, step 6 is obtained are cut into cross section along the impression of mould, obtains fibrous composite and strengthens bar.
The raw materials used commercially available prod that is of this embodiment; The PRM releasing agent converges glad mould sculptured glass steel company available from Guangdong Province; Epoxide-resin glue described in step 2 and the step 4 is to obtain after 100: 30 the mixed by mass ratio by epoxy resin and aromatic amine curing agent; Said epoxy resin and aromatic amine curing agent are available from South Asia, Taiwan company, and said epoxy resin is drawn together flexibilizer and E51 resin.
The beneficial effect of this embodiment is: this embodiment production technology is simple; It is to be processed by Vectran fiber/carbon fiber/Vectran fiber 3-layer composite material that prepared fibrous composite strengthens bar; Corrosion-resistant, anti-aging, and can not be magnetized; Can not produce magnetic torque during as the gravity gradient boom on the satellite, can not exert an influence spacecraft attitude; The carbon fiber that fibrous composite strengthens the bar intermediate layer has high specific strength, high ratio modulus characteristics; Its stretch-proof and bending stiffness are high; Make to strengthen bar and have good elasticity and recoverability, the hot strength that strengthens bar is greater than 1500MPa, the inflation extending arm after the expansion have certain stability; Strengthen sliver transvers section and be designed to arc, improve bending rigidity; The two-layer Vectran fiber up and down that fibrous composite of the present invention strengthens bar has very high toughness, easy fracture not, can make fibrous composite strengthen bar and have less gathering volume.Fibrous composite strengthens the in light weight of bar, and the wide enhancing bar line density of 15mm is less than 15g/m; Fibrous composite enhancing bar linearity of the present invention is high, guarantees that curling the folding of inflation extending arm still has higher linearity after inflating expanded.
The specific embodiment two: what this embodiment and the specific embodiment one were different is: the described particular manufacturing craft of step 6 is made up of formpiston 1 and former 2; Formpiston 1 is provided with boss 3; The surface of boss 3 is provided with a plurality of convex epireliefs 4; Former 2 is provided with groove 5, and the surface of groove 5 is provided with the indenture 6 that is complementary with convex epirelief 4, and the outer contour 7 of the cross section of said convex epirelief 4 forms circular arc.Other is identical with the specific embodiment one.
The specific embodiment three: what this embodiment was different with the specific embodiment one or two is: the surface of said boss 3 is provided with 5～50 convex epireliefs 4.Other is identical with the specific embodiment one or two.
The specific embodiment four: what this embodiment was different with one of specific embodiment one to three is: the length of the pairing string of arc of the outer contour 7 formed circular arcs of the cross section of said convex epirelief 4 is 10～20mm, and this arc place diameter of a circle is 25～40mm.Other is identical with one of specific embodiment one to three.
The specific embodiment five: what this embodiment was different with one of specific embodiment one to four is: the height h1 of said boss 3 and the degree of depth h2 of said groove 5 satisfy relational expression: 0.2mm≤h2-h1≤0.8mm.Other is identical with one of specific embodiment one to four.
The specific embodiment six: what this embodiment was different with one of specific embodiment one to five is: the thickness of said bottom Vectran cloth is 0.1～0.25mm; Top layer Vectran cloth thickness be 0.1～0.25mm, the thickness of carbon cloth is 0.1～0.3mm.Other is identical with one of specific embodiment one to five.
The specific embodiment seven: what this embodiment was different with one of specific embodiment one to six is: said Vectran cloth is 200 dawn plain weave Vectran cloth, and said carbon cloth is the plain weave carbon cloth of 1k.Other is identical with one of specific embodiment one to six.
The specific embodiment eight: what this embodiment was different with one of specific embodiment one to seven is: the width and the length of said bottom Vectran cloth, carbon cloth and bottom Vectran cloth are identical; Width is 10～100cm, and length is 10～1000cm.Other is identical with one of specific embodiment one to seven.
Adopt following examples to verify beneficial effect of the present invention:
Embodiment one:
The preparation method that the present embodiment fibrous composite strengthens bar carries out according to the following steps:
One, shop fixtures layer Vectran cloth: bottom Vectran cloth is tiled on the horizontal operation table top, guarantees that cloth do not have prestressing force in the face;
Two, brush coating: along bottom Vectran cloth length direction, the even brush ring epoxy resins glue on bottom Vectran cloth surface;
Three, intermediate layer, shop carbon cloth: carbon cloth is paved, sticked on the bottom Vectran cloth top of handling, obtain two-layer complex fabric cloth through step 2;
Four, brush coating: arriving of step 3 the even brush ring epoxy resins glue in carbon cloth surface of two-layer complex fabric cloth;
Five, spread a layer Vectran cloth: upper strata Vectran cloth is paved, stick on the carbon cloth top of handling, obtain three layers of complex fabric cloth through step 4;
Six, evenly brush the PRM releasing agent at the formpiston (1) of particular manufacturing craft and the cavity surface of former (2), three layers of composite fibre that step 5 is obtained are arranged in the particular manufacturing craft, and the particular manufacturing craft that three layers of complex fabric cloth will be housed is then put into thermostatic chamber; Heating rate with 2 ℃/h is warming up to 90 ℃; Insulation 2h, the heating rate with 2 ℃/h is warming up to 150 ℃ again, behind the insulation 3h; Naturally cool to room temperature, three layers of complex fabric cloth that obtain solidifying;
It is the rectangular of circular arc that three layers of complex fabric cloth of the curing that seven, step 6 is obtained are cut into cross section along the impression of mould, obtains fibrous composite and strengthens bar.
The prepared fibrous composite of present embodiment strengthens bar and has following character:
It is to be processed by Vectran fiber/carbon fiber/Vectran fiber 3-layer composite material that fibrous composite strengthens bar, corrosion-resistant, anti-aging; Fibrous composite strengthens bar and can not be magnetized, and can not produce magnetic torque during as the gravity gradient boom on the satellite, can not exert an influence to spacecraft attitude; Fibrous composite strengthens sliver transvers section and is designed to arc, improves bending rigidity; The carbon fiber that fibrous composite strengthens the bar intermediate layer has high specific strength, high ratio modulus characteristics; Its stretch-proof and bending stiffness are high; Make to strengthen bar and have good elasticity and recoverability, make certain stability that has of inflation extending arm after the expansion, the hot strength that strengthens bar is 1500MPa; The two-layer Vectran fiber up and down that fibrous composite strengthens bar has very high toughness, easy fracture not; Can make fibrous composite strengthen bar and have less gathering volume; It is 0.3mm that fibrous composite strengthens bar thickness, and folding radius along its length is 25mm; Fibrous composite strengthens the in light weight of bar, and the wide enhancing bar line density of 15mm is 15g/m; Fibrous composite enhancing bar linearity is high, guarantees that curling the folding of inflation extending arm still has higher linearity after inflating expanded.
Claims (8)
1. a fibrous composite strengthens the preparation method of bar, it is characterized in that the preparation method that fibrous composite strengthens bar carries out according to the following steps:
One, shop fixtures layer Vectran cloth: bottom Vectran cloth is tiled on the horizontal operation table top, guarantees that cloth do not have prestressing force in the face;
Two, brush coating: along bottom Vectran cloth length direction, the even brush ring epoxy resins glue on bottom Vectran cloth surface;
Three, intermediate layer, shop carbon cloth: carbon cloth is paved, sticked on the bottom Vectran cloth top of handling, obtain two-layer complex fabric cloth through step 2;
Four, brush coating: arriving of step 3 the even brush ring epoxy resins glue in carbon cloth surface of two-layer complex fabric cloth;
Five, spread a layer Vectran cloth: upper strata Vectran cloth is paved, stick on the carbon cloth top of handling, obtain three layers of complex fabric cloth through step 4;
Six, evenly brush the PRM releasing agent at the formpiston (1) of particular manufacturing craft and the cavity surface of former (2), three layers of composite fibre that step 5 is obtained are arranged in the particular manufacturing craft, and the particular manufacturing craft that three layers of complex fabric cloth will be housed is then put into thermostatic chamber; Heating rate with 1～2 ℃/h is warming up to 90 ℃; Insulation 2h, the heating rate with 1～2 ℃/h is warming up to 150 ℃ again, behind the insulation 3h; Naturally cool to room temperature, three layers of complex fabric cloth that obtain solidifying;
It is the rectangular of circular arc that three layers of complex fabric cloth of the curing that seven, step 6 is obtained are cut into cross section along the impression of mould, obtains fibrous composite and strengthens bar.
2. a kind of fibrous composite according to claim 1 strengthens the preparation method of bar; It is characterized in that the described particular manufacturing craft of step 6 is made up of formpiston (1) and former (2); Formpiston (1) is provided with boss (3), and the surface of boss (3) is provided with a plurality of convex epireliefs (4), and former (2) is provided with groove (5); The surface of groove (5) is provided with the indenture (6) that is complementary with convex epirelief (4), and the outer contour (7) of the cross section of said convex epirelief (4) forms circular arc.
3. a kind of fibrous composite according to claim 2 strengthens the preparation method of bar, it is characterized in that the surface of said boss (3) is provided with 5～50 convex epireliefs (4).
4. a kind of fibrous composite according to claim 2 strengthens the preparation method of bar; The length of the pairing string of arc of the formed circular arc of outer contour (7) that it is characterized in that the cross section of said convex epirelief (4) is 10～20mm, and this arc place diameter of a circle is 25～40mm.
5. a kind of fibrous composite according to claim 2 strengthens the preparation method of bar, it is characterized in that the height h1 of said boss (3) and the degree of depth h2 of said groove (5) satisfy relational expression: 0.2mm≤h2-h1≤0.8mm.
6. a kind of fibrous composite according to claim 1 strengthens the preparation method of bar; The thickness that it is characterized in that said bottom Vectran cloth is 0.1～0.25mm; Top layer Vectran cloth thickness be 0.1～0.25mm, the thickness of carbon cloth is 0.1～0.3mm.
7. a kind of fibrous composite according to claim 1 strengthens the preparation method of bar, it is characterized in that said Vectran cloth is 200 dawn plain weave Vectran cloth, and said carbon cloth is the plain weave carbon cloth of 1k.
8. a kind of fibrous composite according to claim 1 strengthens the preparation method of bar; It is characterized in that said bottom Vectran cloth, carbon cloth are identical with length with the width of top layer Vectran cloth; Width is 10～100cm, and length is 10～1000cm.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201210165676.7A CN102672972B (en) | 2012-05-25 | 2012-05-25 | Preparation method for fiber composite material reinforcing strip |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201210165676.7A CN102672972B (en) | 2012-05-25 | 2012-05-25 | Preparation method for fiber composite material reinforcing strip |
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| CN102672972A true CN102672972A (en) | 2012-09-19 |
| CN102672972B CN102672972B (en) | 2014-05-07 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104249461A (en) * | 2013-06-27 | 2014-12-31 | 蒋娇 | Manufacturing method of glass steel by hand molding |
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|---|---|---|---|---|
| CN1876356A (en) * | 2006-05-26 | 2006-12-13 | 肖忠渊 | Manufacturing flying utensil by using high grade carbon fiber composite material |
| US20080233344A1 (en) * | 2006-02-07 | 2008-09-25 | Burkhart Grob | Airplane component as well as method for manufacturing an airplane component |
| CN101913424A (en) * | 2010-06-24 | 2010-12-15 | 哈尔滨工业大学 | Airship with inflating skeleton expanding in air |
| CN102166856A (en) * | 2010-12-24 | 2011-08-31 | 博睿思科技(大连)有限公司 | Method for processing novel carbon fiber composite board |
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- 2012-05-25 CN CN201210165676.7A patent/CN102672972B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080233344A1 (en) * | 2006-02-07 | 2008-09-25 | Burkhart Grob | Airplane component as well as method for manufacturing an airplane component |
| CN1876356A (en) * | 2006-05-26 | 2006-12-13 | 肖忠渊 | Manufacturing flying utensil by using high grade carbon fiber composite material |
| CN101913424A (en) * | 2010-06-24 | 2010-12-15 | 哈尔滨工业大学 | Airship with inflating skeleton expanding in air |
| CN102166856A (en) * | 2010-12-24 | 2011-08-31 | 博睿思科技(大连)有限公司 | Method for processing novel carbon fiber composite board |
Non-Patent Citations (1)
| Title |
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| 赖光周平: "聚芳酯纤维的特性和应用", 《合成纤维》, vol. 41, no. 1, 31 January 2012 (2012-01-31) * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104249461A (en) * | 2013-06-27 | 2014-12-31 | 蒋娇 | Manufacturing method of glass steel by hand molding |
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